Device for measuring temperature in a primary stream flow passage of a bypass turbojet

Abstract

A device for measuring a compressor inlet temperature in a primary stream flow passage of a bypass turbojet. The device includes an airtight hollow structure forming a connection arm of an intermediate casing of the turbojet and configured to pass radially through a flow passage for the primary stream and a flow passage for a secondary stream of the turbojet, the connection arm including at least one inlet air orifice opening out into the primary stream flow passage at an inlet of a compressor and at least one air outlet orifice leading to a zone of the turbojet in which surrounding pressure is less than pressure in the primary stream flow passage at the inlet of the compressor; and a temperature probe having its sensitive element arranged inside the connection arm.

The invention claimed is: 
     
       1. A device for measuring a compressor inlet temperature in a primary stream flow passage of a bypass turbojet, the device comprising:
 a hollow structure forming a connection arm of an intermediate casing of the turbojet and configured to pass radially through a flow passage for the primary stream and a flow passage for a secondary stream of the turbojet, the connection arm including at least one inlet air orifice opening out into the primary stream flow passage at an inlet of a high pressure compressor and at least one air outlet orifice leading to a zone of the turbojet in which surrounding pressure is less than pressure in the primary stream flow passage at the inlet of the high pressure compressor; and 
 a temperature probe having its sensitive element arranged inside the connection arm. 
 
     
     
       2. A device according to  claim 1 , wherein the connection arm comprises two side walls connected together in an airtight manner, firstly by walls forming a leading edge and a trailing edge, and secondly by transverse walls. 
     
     
       3. A device according to  claim 2 , wherein the air inlet orifice of the connection arm is formed in a side wall and the air outlet orifice is formed in the wall forming the trailing edge. 
     
     
       4. A device according to  claim 2 , wherein the temperature probe is mounted in an airtight manner against the wall of the connection arm that forms the trailing edge. 
     
     
       5. A device according to  claim 2 , further comprising a partition extending radially from one of the transverse walls to improve flow of air around the temperature probe by confining the temperature probe in a restricted space. 
     
     
       6. A device according to  claim 1 , wherein the temperature probe is of pencil type. 
     
     
       7. A device according to  claim 1 , wherein the air outlet orifice of the connection arm is configured to lead into the secondary stream flow passage of the turbojet. 
     
     
       8. An intermediate casing for a bypass turbojet, the casing comprising:
 a hub; 
 an outer annular shroud arranged around the hub, concentrically thereabout; and 
 a device according to  claim 1 , the connection arm of the device connecting the hub radially to the outer shroud. 
 
     
     
       9. An intermediate casing according to  claim 8 , wherein the sensitive element of the temperature probe of the device is arranged inside the connection arm to extend in a direction that is substantially parallel to an axis of revolution of the hub and of the shroud. 
     
     
       10. A bypass turbojet comprising an intermediate casing according to  claim 8 .